ares i first stage: powering exploration - nasa · first stage: powering exploration bruce k....

Ares ONIFirst Stage:

PoweringExploration

Bruce K. TillerAres First Stage Deputy

https://ntrs.nasa.gov/search.jsp?R=20090034468 2019-03-23T13:27:27+00:00Z

Agenda

Introduction

Schedules

First Stage Progress to Date

National Aeronautics and Space Administration

Ares Family of Launch Vehicles

♦ Building on the legacy of the Space Shuttle and other NASA spaceexploration initiatives, the propulsion for the Ares I First Stage will be aShuttle derived reusable solid rocket motor.

♦ Significant progress has been made to date by the Ares First Stage Team.

♦ This brief status provides an update on the design and development of theAres First Stage propulsion system.


Saturn V: 1967–1972

Height 360.0 ft

Gross LiftoffMass (GLOM)

PayloadCapability

DAC 2 TR7 FLV 51.0 0.48

6,500.0K lbm

44.9 mT Trans-LunarInjection (TLI)

118.8 mT to LEO

Building on 50 Years of Proven Experience– Launch Vehicle Comparisons – .

Space Shuttle: 1981–Present Ares I: First Flight 2015

184.2 ft 325.0 ft

400

300

m

2dvt

200

O

100

rew

LunarLander

S-IVB(One J-2 LiquidOxygen/LiquidHydrogen(LOX/LH2)

engine)S-II(Five J-2 LOX/LH2 engines)

S-IC(Five F-1 LOX/RP-1 engines)

d 'fTwo 4-SegmentZ Reusable SolidRocket Boosters

© (RSRBs)

4,500.0K lbm

25.0 mT to LEO

ltair

arth Departuretage (1 J-2XOX/LH2 engine)

Core Stage(Six RS-68LOX/LH2

engines)

Orion

' Upper Stage(One J-2XLOX/LH2 engine)

.I'o^

One 5-SegmentRSRB

2,057.3K lbm

24.9 mT to LEO

tt Two 5.5-SegmentL RSRBss ^ +R 1 .a.

Ares V: First Flight 2018

381.1 ft

8,167.1 K lbm

71.1 mT to TLI with Ares I62.8 mT to TLI

~187.7 mT to LEO


Ares I Acquisition Model

DAC 2 TR 7

Ace Administration

Orion Crew *,

Upper Stage Enginee Pratt and Whitney Rocketdyne

Instrument Unite NASA Design/

Qoeing Production

First Stagee ATK Launch Systems

Aft Skirt

Ares I First Stage Overview

♦ Legacy motor casings, aft skirt

♦ New forward structures• Forward Skirt• Forward Skirt Extension• Aeroshell• Frustum

♦ Metal and composite materials

♦ Shuttle-derived five-segment solidrocket motor

• Increased performance• Extensibility to Ares V

Frustum

Aeroshell

Forward Skirt Extension

Forward Skirt

Ui7

Q1Solid RocketMotor Segments

Ir

IM

iITZ5

Nozzle

Time

! Thrust trace comparison: Shuttle versus Ares I


Asbestos free insulation/liner

C-Spring isolators

Wide throat nozzleBooster DecelerationMotors (from Shuttle)


Same cases andjoints as Shuttle

Ares I First Stage

Tumble Motors(from Shuttle)

Same propellantas Shuttle (PBAN)-

optimized forAres application

New 150 ft diameter parachutes

Modern electronics

Same aft skirt and thrust vectorcontrol as Shuttle

DAC 2 TR 7

% A

Propellant chamfers on aft andcenter segments Wider throat and nozzle

extension for increasedmass flow

Modified height and thickness toprevent bore choking

Ares First Stage Upgrades

Zit Increased number of finsfrom 11 to 12 in fwd

- -, - segment

....^..^^:^ Burn rate lowered to meetI Ares I requirements

Modifications to the motor weremade to:

• Improve performance (thrust)• Improve reliability• Eliminate hazardous materials• Replace obsolete materials

Added Segment

Insulation and liner formulations modified toeliminate Chrysotile fibersLay-up optimized to provide additional thermalprotection


SpacecraftSeparation

ESM Panel JettisonTime = 154.1 sec

Altitude = 79,500 m (260.8K ft)Mach = 6.51

Launch Abort System(LAS) Jettison

Time = 157.1 secAltitude = 81,667 m (267.9K ft)

Mach = 6.59

Upper StageReentry and

FSB Reentry

Breakupand Descent

Ares I Lunar Mission Profile

Solid Rocket Booster(SRB) Separation

Time 125.9 secAltitude 57,106 m (187.4K ft)

Mach 5.69Max Altitude 100,452 m (329.6K ft)

Dynamic Pressure = 0.7 kN/m 2

^. (15.6 psf)

Maximum AxialAcceleration

3.73 gTime = 104.0 sec


Dyn. Press. = 6.4 kN/m2

(134.1 psf) '

Orbital InsertionAltitude = 129,600 m (70 nmi))

–20.4 x 185,200 m(–11.0 x 100.0 nmi)

Main Engine Cutoff (MECO)Time = 593.9 sec

Burn Duration = 466.0 sec

-F

Main Engine StartTime = 127.8 sec


Maximum Dynamic PressureTime = 59.0 sec


Dynamic Pressure = 359.9 kN/m 2

(749.6 psf)

LiftoffT

Time = 0.6 secLaunch Thrust-to-Weight Ratio = 1.56

Gross Liftoff Mass (GLOM) =933.2 mT (2,057.3K lbm)

DAC 2 TR 7


ESM – Encapsulated Service ModuleFSB – Forward Segment Booster

GLOM – Gross Liftoff MassLAS – Launch Abort System

MECO – Main Engine CutoffSRB – Solid Rocket Booster

US – Upper Stage

SRBSplashdown


Upper StageImpact

(Indian Ocean)

Ares I First Sta ge DDT&E Schedule

ARES Milestones SRR Q SDR Q PDR 1X Ares CDR 1 Jul Ares CDR 2Sep I-Y Or-1 Q DCR 4DecOct Aug Aug Mar Sep Jan

First Stage re-SRR TIM SRR PDR FS CDR QRR DCRIP

Aug Dec Jun AprApr NovMilestones

MSI/MSLGVT H/W Deliveries Aft Skirts O QNov QFwd Structures I

Jul Oct

1 Fab DM-1 Test (N)

Motors Fab ReviewOct Aug DM-2 Test (C) I

s`

Fab1st Cast Jas DM-3 Test (H)

F1st Cast

Sep DM-4 Test (N) I} M Fab

1st Cast Mar

QualificationCommit

. .Fab QM-1 Test (N)

to QM 0Motorsr .

Fab Review 1st Cast Jun QM-2 Test (C) IFab

t Cast DecQM-3 Test (H)Fa

1

^1st Cast Jun

Start Ares IX Deliveries

Ares IX &

Flt Test Motors

Ares IX Design & Fab to KSC Aft

RSRMSid

Mar

Ares 1Y Motor Fab Ares 1Y O/D

Fwd Assy 1stCast Dec Orion 1 O/D& 5SS Orion 1 Motor Fab

1st Cast Jun Orion 2 O/D

0

Orion 2 Motor FabT.O. T.O. 1st Cast Dec

PDR CheckpointTIM Delta PDR CDRSE&I DCR

MS CD TIMStructures

CD TimsSep & Decel

CD TIMTesting Complete

AvionicsCD TIM

Qual Testing Complete

TVCCD TIM

FSSHIL Development V&V Testing Dev Testing Complete

HILDesign Rev CD TIM Qual Testing Complete

PyroInteg PSR 1Y Stage Assy Or-2 Stage Assy

Assembly IntegrationOr-1 Stage Assy

First Stage Progress to Date

♦ Successful Preliminary Design Review Completed inJune, 2008

I, ♦ Major Test Programs• Parachute drop tests• Stage separation pyrotechnics

• Development motor (scheduled for August, 25 2009)

' ♦ Several Major Items Manufactured• Ares I-X motor segments

i • Development motor (DM-1) Nozzle• DM-1 segments completed and motor installed in T-97 Test Stand• through insulation• Insulation lay-up has begun on DM-2 segments

♦ Ares 1-X Support ' • Completed all Hardware Acceptance Reviews

• Motor segments were completed and shipped to KSC in March 2009' • All hardware has been transferred to Ground Ops

• Hardware being mated at KSC


First Stage Thrust Oscillation

♦ June Program Review was completed with decision to baseline andimplement Dual Plane (DP) Isolation

• Baseline design established as a DP isolation system with the first planebetween first stage and upper stage with a reference stiffness of 8M lb/in and anupper plane between US and Orion, on the US side of the interface with areference stiffness of 1.2M lb/in

• Upper Stage will begin design efforts to include the second plane isolator andcoordinate interface design requirements with Orion

Four basic ways to attack problem:♦ Reduce forcing function

.— Respo

♦ Detune system response away from forcing functionfrequency

♦ Actively create an opposingThrustforcing function Structural fun

♦ Passively absorb forcing function mode

♦ Mitigation Options ♦ Baseline Design

National Aeronautics and Space Administration7764.12

parison of Mitigation Options

Risk Mitigation Options

National Aeronautics and Space Administration7764.13

tum Separationmontory, UT

utics and Space Administration

Test

Cluster Drop Test (CDT)-1Yuma Proving Grounds, AZ


First Stage Accomplishments

Ares I-X Super StackKennedy Space Center, FL

nd Space Administration

to Aft Booster on M LP

and Space Administration

DM-1 Fwd Segment CastingPromontory, UT

DM-1 Segment ProcessingCasting/X-ray Operations


DMA C/A Segment CastingPromontory, UT

DM-1 Aft Segment Castingr- v Promontory, UT

Built-up Thrust Vector Control/Discrete Interface

ccomplishments

Thrust Oscillation Flexure Design (A) and Testing (B)San Luis Obispo, CA

DM-1 Installation into Test StandPromontory, UT

s and Space Administration

DM-1 in T-97 Test Stand ' tS4

Promontory, UTi i -

Conclusion

res First Stage design is on schedule♦ Avionics

♦ Major Structures

♦ Motor

♦ Deceleration System

res I-X hardware is complete and assembly at KSC isunderway

♦ Launch scheduled for October 31.

♦ Recovery system testing is on schedule♦ Drogue

♦ Main chuteL

♦ Cluster

♦ DM-1 static firing is scheduled for August 25, 2009

Development Motor #1 (DM-1)August 25, 2009

ares i first stage: powering exploration - nasa · first stage: powering exploration bruce k....

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